WO2006108579B1 - Single slotted flap with sliding deflector flap and lowerable spoiler - Google Patents

Single slotted flap with sliding deflector flap and lowerable spoiler

Info

Publication number
WO2006108579B1
WO2006108579B1 PCT/EP2006/003212 EP2006003212W WO2006108579B1 WO 2006108579 B1 WO2006108579 B1 WO 2006108579B1 EP 2006003212 W EP2006003212 W EP 2006003212W WO 2006108579 B1 WO2006108579 B1 WO 2006108579B1
Authority
WO
WIPO (PCT)
Prior art keywords
slot
high lift
wing element
slot covering
lift device
Prior art date
Application number
PCT/EP2006/003212
Other languages
French (fr)
Other versions
WO2006108579A1 (en
Inventor
Klaus Bender
Ole Boettger
Original Assignee
Airbus Gmbh
Klaus Bender
Ole Boettger
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Gmbh, Klaus Bender, Ole Boettger filed Critical Airbus Gmbh
Priority to CN200680011499XA priority Critical patent/CN101155726B/en
Priority to US11/911,124 priority patent/US8066228B2/en
Priority to DE602006019702T priority patent/DE602006019702D1/en
Priority to BRPI0607925-3A priority patent/BRPI0607925A2/en
Priority to JP2008504700A priority patent/JP5185105B2/en
Priority to CA2598419A priority patent/CA2598419C/en
Priority to EP06724150A priority patent/EP1868887B1/en
Publication of WO2006108579A1 publication Critical patent/WO2006108579A1/en
Publication of WO2006108579B1 publication Critical patent/WO2006108579B1/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
    • B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
    • B64C9/20—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing by multiple flaps
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/02—Mounting or supporting thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
    • B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
    • B64C9/18—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing by single flaps
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C9/00—Adjustable control surfaces or members, e.g. rudders
    • B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
    • B64C2009/143—Adjustable control surfaces or members, e.g. rudders forming slots comprising independently adjustable elements for closing or opening the slot between the main wing and leading or trailing edge flaps
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Fittings On The Vehicle Exterior For Carrying Loads, And Devices For Holding Or Mounting Articles (AREA)
  • Toys (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Mechanical Control Devices (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Abstract

The present invention relates to a device for adjusting the lift characteristics of an aircraft with a high lift device (2) that is movably attachable to a wing element (1) and that comprises at least one slot covering device (3; 4), wherein the at least one slot covering device (3; 4), is movably attachable to the wing element (1). The slot covering device (3; 4) is designed to regulate the size of a slot (7) between the wing element (1) and the high lift device (2).

Claims

AMENDED CLAIMS received by the International Bureau on 26 Oct 2006
1. A device for adjusting the lift characteristics of an aircraft, comprising: a high lift device (2); at least one slot covering device (3;4)j wherein the high lift device (2) is movably attachable to a wing element (1); wherein the at least one slot covering device (3;4) is movably attachable to the wing element (1); wherein at least one slot covering device (3;4) of the at least one slot covering devices is movably and controllably attached on fhe underside of the wing element (1) to regulate the size of the slot (7) between the wing element (1) and the high lift device (2); wherein at least one slot covering device (3; 4) of the at least one slot covering devices is movably and controllably attached to the top of the wing element to regulate the size of the slot (7) between the wing element (1) and the high lift device (2); and wherein the at least one slot covering device (3;4) is designed to regulate the size of a slot (T) between the wing element (1) and the high lift device (2).
2. The device of claim 1, further comprising the wing element (1),
3 The device of any one of the preceding claims, wherein the at least one slot covering device (3;4) is attachable so as to be rotatable on the longitudinal axis of the wing element (1),
4. The device of any one of claims 2 or 3, wherein the at least pne slot covering device (3;4) is retractable into an indentation (8) in. the wing element (i).
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5. The device of any one of claims 2 to 4, wherein the high lift device (2) is movably attached to the rear region (5) of the wing element (1).
6. The device of any one of claims 2 to 5, wherein the high lift device (2) is niovably attached to the front region of the wing element (1).
7. The device of any one of claims 2 to 6, wherein the high lift device (2) can he hinged downward from the wing element (1).
8. The device of any one of claims 2 to 7, wherein the high lift device (2) can be extended rearward from the wing element (1).
9. The device of any one of the preceding claims, wherein the device comprises a rail-supported structure for controlling the high lift device (2) and/or the at least one slot covering device (3;4).
10. The device of any one of the preceding claims, comprising a structure supported by multiple guide rods for controlling the high lift device (2) and/or the at least one slot covering device (3;4).
11. The device of any one of the preceding claims, wherein the high lift device (2) is selected from the group comprising wing flaps, single slotted flaps, Fowler flaps, double slotted flaps, triple slotted flaps, Fester slats and Handley Page slats.
12. A method for adjusting the lift characteristics of an aircraft, wherein according to the method by means of a slot covering device (3:4) the size of a slot (7) between a wing element (1) and a high lift device (2) is regulated,
13. The method of claim 14, wherein during the takeoff phase and/or the landing phase of an aircraft the high lift device (2) is extended rearward and/or hinged downward.
14. The method of claim 12 or 13, wherein the slot (7) is closed during the takeoff phase by means of the slot covering device (3:4).
15. The method of any one of claims 12 to 14, wherein during the landing phase of an aircraft the high lift device (2) is extended rearward and/or hinged downward,
16. The method of any one of claims 12 to 15, wherein during a landing phase the slot covering device (3:4) controls the slot (7) such that stalling is prevented.
17. The method of any one of claims 12 to 16, wherein the slot covering device (3;4) and/or the high lift device (2) are/is controlled by an on-board computer.
I8. The method of claim 17, wherein the control parameters of the on-board computer are selected from the group comprising flight speed, angle of attach, wing profile, air pressure, temperature and flight altitude.
19. A means of locomotion comprising a device for adjusting the lift characteristics of one of claims 1 to 11,
20. The means of locomotion of claim 19, wherein the means of locomotion is an aircraft.
21. The use of a device for adjusting the lift characteristics of any one of claims 1 to 11 in an aircraft.
PCT/EP2006/003212 2005-04-11 2006-04-07 Single slotted flap with sliding deflector flap and lowerable spoiler WO2006108579A1 (en)

Priority Applications (7)

Application Number Priority Date Filing Date Title
CN200680011499XA CN101155726B (en) 2005-04-11 2006-04-07 Device and method for adjusting lift characteristic of aircraft
US11/911,124 US8066228B2 (en) 2005-04-11 2006-04-07 Single slotted flap with sliding deflector flap and lowerable spoiler
DE602006019702T DE602006019702D1 (en) 2005-04-11 2006-04-07 SINGLE-FOLDING FLAP WITH SLIDING REAR FLAP AND SLEEPABLE SPOILER
BRPI0607925-3A BRPI0607925A2 (en) 2005-04-11 2006-04-07 single slotted flap with sliding deflector flap and lowering spoiler
JP2008504700A JP5185105B2 (en) 2005-04-11 2006-04-07 Single slotted flap with sliding deflector flap and lowering spoiler
CA2598419A CA2598419C (en) 2005-04-11 2006-04-07 Single slotted flap with sliding deflector flap and lowerable spoiler
EP06724150A EP1868887B1 (en) 2005-04-11 2006-04-07 Single slotted flap with sliding deflector flap and lowerable spoiler

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US67020105P 2005-04-11 2005-04-11
US60/670,201 2005-04-11
DE102005016578A DE102005016578A1 (en) 2005-04-11 2005-04-11 Airplane`s lift characteristics adjusting device, has spoiler devices movably fastened at wing unit and/or at high lift device, where spoiler devices are designed such that size of gap between wing unit and high lift device is adjusted
DE102005016578.8 2005-04-11

Publications (2)

Publication Number Publication Date
WO2006108579A1 WO2006108579A1 (en) 2006-10-19
WO2006108579B1 true WO2006108579B1 (en) 2007-01-11

Family

ID=37055256

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2006/003212 WO2006108579A1 (en) 2005-04-11 2006-04-07 Single slotted flap with sliding deflector flap and lowerable spoiler

Country Status (9)

Country Link
US (1) US8066228B2 (en)
EP (1) EP1868887B1 (en)
JP (1) JP5185105B2 (en)
CN (1) CN101155726B (en)
BR (1) BRPI0607925A2 (en)
CA (1) CA2598419C (en)
DE (2) DE102005016578A1 (en)
RU (1) RU2399553C2 (en)
WO (1) WO2006108579A1 (en)

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DE102006053259A1 (en) * 2006-11-11 2008-05-21 Airbus Deutschland Gmbh High-lift system on the wing of an aircraft and method for its operation
US7874524B2 (en) * 2007-11-16 2011-01-25 The Boeing Company Methods and apparatus for a multi-segment flap fence
FR2929724B1 (en) * 2008-04-02 2010-04-30 Airbus France METHOD FOR DETERMINING THE FLOOD OUTPUT SPEED OF AN AIRCRAFT.
GB0810724D0 (en) * 2008-06-12 2008-07-16 Airbus Uk Ltd Slat assembly
DE102008033005A1 (en) * 2008-07-14 2010-03-18 Airbus Deutschland Gmbh Aerodynamic flap and wings
US8424810B1 (en) 2010-03-31 2013-04-23 The Boeing Company Low noise wing slat system with rigid cove-filled slat
US8276852B2 (en) * 2010-03-31 2012-10-02 The Boeing Company Low noise wing slat system with deployable wing leading edge elements
US8864083B1 (en) 2010-03-31 2014-10-21 The Boeing Company Low noise wing slat system with a fixed wing leading edge and deployable bridging panels
GB201117340D0 (en) 2011-10-07 2011-11-23 Airbus Uk Ltd Flat support
GB2512318A (en) * 2013-03-26 2014-10-01 Eads Uk Ltd Lift-reducing apparatus for aircraft wings
US10000274B2 (en) * 2015-08-20 2018-06-19 The Boeing Company Mitigation of surface discontinuities between flight control surfaces and an airframe of an aircraft
US11046425B2 (en) * 2016-05-20 2021-06-29 Bombardier Inc. Apparatus and methods for actuating a double-slotted flap using a slave screw
CN108100223A (en) * 2017-11-29 2018-06-01 中国航空工业集团公司西安飞机设计研究所 A kind of whirlpool paddle aircraft
GB2579221A (en) * 2018-11-26 2020-06-17 Airbus Operations Ltd Aircraft control mechanism
EP3941828A4 (en) 2019-03-21 2022-11-16 AMSL Innovations Pty Ltd Vertical take-off and landing (vtol) aircraft
CN110866351B (en) * 2019-09-27 2021-07-27 南京航空航天大学 Resistance-increasing micro-texture design of wing spoiler and manufacturing method based on CFRP material
CN110861767A (en) * 2019-12-13 2020-03-06 贵州贵航飞机设计研究所 Method for combined driving of wing high-lift device
CN113104196B (en) * 2021-05-28 2022-05-24 中国商用飞机有限责任公司 High-lift device and high-lift method for aircraft
CN114750930B (en) * 2022-05-07 2023-05-16 中国航空工业集团公司沈阳飞机设计研究所 Airfoil slotted spoiler type course control surface

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Also Published As

Publication number Publication date
DE602006019702D1 (en) 2011-03-03
BRPI0607925A2 (en) 2009-10-20
CA2598419C (en) 2013-07-23
US8066228B2 (en) 2011-11-29
RU2007141590A (en) 2009-05-20
WO2006108579A1 (en) 2006-10-19
CN101155726A (en) 2008-04-02
CN101155726B (en) 2013-03-13
CA2598419A1 (en) 2006-10-19
JP5185105B2 (en) 2013-04-17
EP1868887A1 (en) 2007-12-26
JP2008535721A (en) 2008-09-04
US20080179464A1 (en) 2008-07-31
EP1868887B1 (en) 2011-01-19
DE102005016578A1 (en) 2006-10-19
RU2399553C2 (en) 2010-09-20

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